def createFlapStructure(myFlap, maxX=0.4, innerHingeXsi=0.7, outerHingeXsi=0.7, appendInnerCruiseRoller=False, type='flap', innerX=0., outerX=0.):
myUID = myFlap.get_uID()
# Structure
createShell(myFlap, myUID, type, thickness=0.001)
createSpars(myFlap, myUID, type)
createRibs(myFlap, myUID, type, thickness=0.001, nRibs=20)
# Moveables
createTracks(myFlap, type, myUID)
createPath(myFlap, type, myUID, innerX, outerX, innerHingeXsi, outerHingeXsi)
if appendInnerCruiseRoller:
createCruiseRollers(myFlap, 'outerFlap', myUID + '_CR1')
def createFlapStructure(myFlap,
maxX=0.4,
innerHingeXsi=0.7,
outerHingeXsi=0.7,
appendInnerCruiseRoller=False,
type='flap',
innerX=0.,
outerX=0.):
myUID = myFlap.get_uID()
# Structure
createShell(myFlap, myUID, type, thickness=0.001)
createSpars(myFlap, myUID, type)
createRibs(myFlap, myUID, type, thickness=0.001, nRibs=20)
# Moveables
createTracks(myFlap, type, myUID)
createPath(myFlap, type, myUID, innerX, outerX, innerHingeXsi,
outerHingeXsi)
if appendInnerCruiseRoller:
createCruiseRollers(myFlap, 'outerFlap', myUID + '_CR1')
def createAileron(parentWingCPACS, parentWingVAMPzero, myAileron):
'''
This is the main export method for the wings aileron
'''
cpacsPath = '/cpacs/vehicles/aircraft/model/wings/wing[' + parentWingVAMPzero.id + ']'
cpacsWing = getObjfromXpath(parentWingCPACS, cpacsPath)
cpacsComponentSegment = cpacsWing.get_componentSegments().get_componentSegment()[0]
# Header
myName = stringBaseType(None, None, None, 'aileron')
myDescription = stringBaseType(None, None, None, 'aileron from VAMPzero')
myParentUID = stringUIDBaseType(None, None, 'True', None, 'wing_Cseg')
# Initialization, i.e. fetching values throughout the code
xsis = []
etas = []
for i in range(3,7):
try:
xsis.append(eval(cpacsComponentSegment.get_structure().get_spars().get_sparPositions().get_sparPosition()[i].get_xsi().valueOf_))
etas.append(eval(cpacsComponentSegment.get_structure().get_spars().get_sparPositions().get_sparPosition()[i].get_eta().valueOf_))
except IndexError:
pass
xsiSpar_interp = scipy.interpolate.interp1d(etas, xsis)
sparOffset = 0.1
wingSpan = parentWingVAMPzero.span.getValue() / 2.
# Outer Shape
# The outer border eta station is set to 96 percent
outerEtaLE = 0.96
# The outer chord station is determined from the wing's chord at eta = 0.96
# and the rear spar location + the spar offset
outerXsiLE = xsiSpar_interp(0.96) + sparOffset
outerWingChord = calcChordLengthAtEta(outerEtaLE, parentWingVAMPzero, cpacsWing)
cTip = (1 - outerXsiLE) * outerWingChord
# now we need to determine the necessary span for the aileron by gently increasing the span
# this is an iterative process as the chord of the aileron is a function of the inbound span
aileronArea = parentWingVAMPzero.aileron.refArea.getValue()
delta = 0.01
calcArea = 0.
while abs(calcArea - aileronArea) > 0.1:
if delta > outerEtaLE:
parentWingVAMPzero.log.warning('VAMPzero EXPORT: Cannot determine the span of the aileron')
parentWingVAMPzero.log.warning('VAMPzero EXPORT: aileronArea= '+str(aileronArea))
parentWingVAMPzero.log.warning('VAMPzero EXPORT: Decreasing Spar Offset')
sparOffset = sparOffset - 0.02
delta = 0.01
innerEtaLE = outerEtaLE - delta
innerXsiLE = xsiSpar_interp(innerEtaLE) + sparOffset
innerWingChord = calcChordLengthAtEta(innerEtaLE, parentWingVAMPzero, cpacsWing)
cRoot = (1 - innerXsiLE) * innerWingChord
calcArea = (cTip + cRoot) / 2 * (outerEtaLE - innerEtaLE) * wingSpan
delta += 0.005
# start outer shape
myleadingEdgeShape = leadingEdgeShapeType(relHeightLE=doubleBaseType(valueOf_=str(0.5)), xsiUpperSkin=doubleBaseType(valueOf_=str(0.85)), xsiLowerSkin=doubleBaseType(valueOf_=str(0.85)))
innerBorder = controlSurfaceBorderTrailingEdgeType(etaLE=doubleBaseType(valueOf_=str(innerEtaLE)), etaTE=doubleBaseType(valueOf_=str(innerEtaLE)), xsiLE=doubleBaseType(valueOf_=str(innerXsiLE)), leadingEdgeShape=myleadingEdgeShape)
outerBorder = controlSurfaceBorderTrailingEdgeType(etaLE=doubleBaseType(valueOf_=str(outerEtaLE)), etaTE=doubleBaseType(valueOf_=str(outerEtaLE)), xsiLE=doubleBaseType(valueOf_=str(outerXsiLE)), leadingEdgeShape=myleadingEdgeShape)
myOuterShape = controlSurfaceOuterShapeTrailingEdgeType(innerBorder=innerBorder, outerBorder=outerBorder)
# structure
myStructure = wingComponentSegmentStructureType()
cpacsAileron = trailingEdgeDeviceType(uID='aileronUID', name=myName, description=myDescription, parentUID=myParentUID, outerShape=myOuterShape, structure=myStructure)
createAileronStructure(cpacsAileron)
# Forward information about innerEtaLE to the flap
parentWingVAMPzero.flap.maxEta = parameter(value=innerEtaLE, doc='This it the inner position of the aileron, the flap may not exceed it')
# moveables
deltaEta = outerEtaLE - innerEtaLE
innerParentXsi = xsiSpar_interp(innerEtaLE + 0.3 * deltaEta) + 0.02
outerParentXsi = xsiSpar_interp(innerEtaLE + 0.7 * deltaEta) + 0.02
createPath(cpacsAileron, 'aileron')
createTracks(cpacsAileron, 'aileron')
createActuators(cpacsAileron, 'aileron', [innerParentXsi, outerParentXsi])
if type(cpacsComponentSegment.get_controlSurfaces()) == NoneType:
cpacsComponentSegment.set_controlSurfaces(controlSurfacesType())
if type(cpacsComponentSegment.get_controlSurfaces().get_trailingEdgeDevices()) == NoneType:
cpacsComponentSegment.get_controlSurfaces().set_trailingEdgeDevices(trailingEdgeDevicesType())
cpacsComponentSegment.get_controlSurfaces().get_trailingEdgeDevices().add_trailingEdgeDevice(cpacsAileron)
def createAileron(parentWingCPACS, parentWingVAMPzero, myAileron):
'''
This is the main export method for the wings aileron
'''
cpacsPath = '/cpacs/vehicles/aircraft/model/wings/wing[' + parentWingVAMPzero.id + ']'
cpacsWing = getObjfromXpath(parentWingCPACS, cpacsPath)
cpacsComponentSegment = cpacsWing.get_componentSegments(
).get_componentSegment()[0]
#===========================================================================
# Header
#===========================================================================
myName = stringBaseType(None, None, None, 'aileron')
myDescription = stringBaseType(None, None, None, 'aileron from VAMPzero')
myParentUID = stringUIDBaseType(None, None, 'True', None, 'wing_Cseg')
#===========================================================================
# Initialization, i.e. fetching values throughout the code
#===========================================================================
xsiSparRoot = eval(cpacsComponentSegment.get_structure().get_spars(
).get_sparPositions().get_sparPosition()[3].get_xsi().valueOf_)
xsiSparFuselage = eval(cpacsComponentSegment.get_structure().get_spars(
).get_sparPositions().get_sparPosition()[4].get_xsi().valueOf_)
xsiSparKink = eval(cpacsComponentSegment.get_structure().get_spars(
).get_sparPositions().get_sparPosition()[5].get_xsi().valueOf_)
xsiSparTip = eval(cpacsComponentSegment.get_structure().get_spars(
).get_sparPositions().get_sparPosition()[6].get_xsi().valueOf_)
etaSparRoot = eval(cpacsComponentSegment.get_structure().get_spars(
).get_sparPositions().get_sparPosition()[3].get_eta().valueOf_)
etaSparFuselage = eval(cpacsComponentSegment.get_structure().get_spars(
).get_sparPositions().get_sparPosition()[4].get_eta().valueOf_)
etaSparKink = eval(cpacsComponentSegment.get_structure().get_spars(
).get_sparPositions().get_sparPosition()[5].get_eta().valueOf_)
etaSparTip = eval(cpacsComponentSegment.get_structure().get_spars(
).get_sparPositions().get_sparPosition()[6].get_eta().valueOf_)
xsiSpar_interp = scipy.interpolate.interp1d(
[etaSparRoot, etaSparFuselage, etaSparKink, etaSparTip],
[xsiSparRoot, xsiSparFuselage, xsiSparKink, xsiSparTip])
sparOffset = 0.1
wingSpan = parentWingVAMPzero.span.getValue() / 2.
#===========================================================================
# Outer Shape
#===========================================================================
# The outer border eta station is set to 96 percent
outerEtaLE = 0.96
# The outer chord station is determined from the wing's chord at eta = 0.96
# and the rear spar location + the spar offset
outerXsiLE = xsiSpar_interp(0.96) + sparOffset
outerWingChord = calcChordLengthAtEta(outerEtaLE, parentWingVAMPzero,
cpacsWing)
cTip = (1 - outerXsiLE) * outerWingChord
# now we need to determine the necessary span for the aileron by gently increasing the span
# this is an iterative process as the chord of the aileron is a function of the inbound span
aileronArea = parentWingVAMPzero.aileron.refArea.getValue()
delta = 0.01
calcArea = 0.
while abs(calcArea - aileronArea) > 0.1:
if delta > outerEtaLE:
parentWingVAMPzero.log.warning(
'VAMPzero EXPORT: Cannot determine the span of the aileron')
parentWingVAMPzero.log.warning('VAMPzero EXPORT: aileronArea= ' +
str(aileronArea))
parentWingVAMPzero.log.warning(
'VAMPzero EXPORT: Decreasing Spar Offset')
sparOffset = sparOffset - 0.02
delta = 0.01
innerEtaLE = outerEtaLE - delta
innerXsiLE = xsiSpar_interp(innerEtaLE) + sparOffset
innerWingChord = calcChordLengthAtEta(innerEtaLE, parentWingVAMPzero,
cpacsWing)
cRoot = (1 - innerXsiLE) * innerWingChord
calcArea = (cTip + cRoot) / 2 * (outerEtaLE - innerEtaLE) * wingSpan
delta += 0.005
# start outer shape
myleadingEdgeShape = leadingEdgeShapeType(
relHeightLE=doubleBaseType(valueOf_=str(0.5)),
xsiUpperSkin=doubleBaseType(valueOf_=str(0.85)),
xsiLowerSkin=doubleBaseType(valueOf_=str(0.85)))
innerBorder = controlSurfaceBorderTrailingEdgeType(
etaLE=doubleBaseType(valueOf_=str(innerEtaLE)),
etaTE=doubleBaseType(valueOf_=str(innerEtaLE)),
xsiLE=doubleBaseType(valueOf_=str(innerXsiLE)),
leadingEdgeShape=myleadingEdgeShape)
outerBorder = controlSurfaceBorderTrailingEdgeType(
etaLE=doubleBaseType(valueOf_=str(outerEtaLE)),
etaTE=doubleBaseType(valueOf_=str(outerEtaLE)),
xsiLE=doubleBaseType(valueOf_=str(outerXsiLE)),
leadingEdgeShape=myleadingEdgeShape)
myOuterShape = controlSurfaceOuterShapeTrailingEdgeType(
innerBorder=innerBorder, outerBorder=outerBorder)
# structure
myStructure = wingComponentSegmentStructureType()
cpacsAileron = trailingEdgeDeviceType(uID='aileronUID',
name=myName,
description=myDescription,
parentUID=myParentUID,
outerShape=myOuterShape,
structure=myStructure)
createAileronStructure(cpacsAileron)
# Forward information about innerEtaLE to the flap
parentWingVAMPzero.flap.maxEta = parameter(
value=innerEtaLE,
doc=
'This it the inner position of the aileron, the flap may not exceed it'
)
# moveables
deltaEta = outerEtaLE - innerEtaLE
innerParentXsi = xsiSpar_interp(innerEtaLE + 0.3 * deltaEta) + 0.02
outerParentXsi = xsiSpar_interp(innerEtaLE + 0.7 * deltaEta) + 0.02
createPath(cpacsAileron, 'aileron')
createTracks(cpacsAileron, 'aileron')
createActuators(cpacsAileron, 'aileron', [innerParentXsi, outerParentXsi])
if type(cpacsComponentSegment.get_controlSurfaces()) == NoneType:
cpacsComponentSegment.set_controlSurfaces(controlSurfacesType())
if type(cpacsComponentSegment.get_controlSurfaces().
get_trailingEdgeDevices()) == NoneType:
cpacsComponentSegment.get_controlSurfaces().set_trailingEdgeDevices(
trailingEdgeDevicesType())
cpacsComponentSegment.get_controlSurfaces().get_trailingEdgeDevices(
).add_trailingEdgeDevice(cpacsAileron)
